FX74_CL5_140 (fx74cl5140-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX74_CL5_140 (fx74cl5140-il) Reynolds number: 200,000 Max Cl/Cd: 73.76 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74cl5140-il-200000-n5.txt Download as CSV file: xf-fx74cl5140-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX74_CL5_140
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2827 0.09895 0.09253 -0.1336 0.5427 0.0164
-9.500 0.2916 0.09683 0.09041 -0.1345 0.5404 0.0168
-9.250 0.3005 0.09480 0.08838 -0.1353 0.5379 0.0169
-9.000 0.3085 0.09287 0.08646 -0.1364 0.5360 0.0171
-8.750 0.3165 0.09101 0.08458 -0.1372 0.5338 0.0172
-8.500 0.3232 0.08926 0.08282 -0.1383 0.5323 0.0173
-8.250 0.3334 0.08684 0.08038 -0.1386 0.5305 0.0174
-8.000 0.3441 0.08457 0.07810 -0.1387 0.5285 0.0178
-7.750 0.3534 0.08262 0.07618 -0.1392 0.5266 0.0180
-7.500 0.3624 0.08074 0.07431 -0.1396 0.5247 0.0182
-7.250 0.3711 0.07883 0.07242 -0.1401 0.5230 0.0189
-7.000 0.3794 0.07699 0.07060 -0.1405 0.5214 0.0192
-6.750 0.3866 0.07514 0.06877 -0.1409 0.5199 0.0201
-6.500 0.3923 0.07350 0.06715 -0.1414 0.5185 0.0205
-6.250 0.3902 0.07242 0.06611 -0.1418 0.5173 0.0208
-6.000 0.4043 0.06986 0.06353 -0.1410 0.5158 0.0215
-5.750 0.4106 0.06837 0.06204 -0.1406 0.5145 0.0222
-5.500 0.4189 0.06675 0.06042 -0.1411 0.5133 0.0232
-5.250 0.4284 0.06499 0.05867 -0.1423 0.5121 0.0240
-5.000 0.4404 0.06305 0.05678 -0.1458 0.5108 0.0248
-4.750 0.4596 0.06067 0.05441 -0.1522 0.5094 0.0250
-4.500 0.4726 0.05837 0.05214 -0.1526 0.5078 0.0253
-4.250 0.4847 0.05651 0.05030 -0.1519 0.5062 0.0259
-4.000 0.5026 0.05447 0.04825 -0.1541 0.5046 0.0267
-3.750 0.5256 0.05215 0.04591 -0.1582 0.5030 0.0278
-3.500 0.5809 0.04794 0.04152 -0.1737 0.5015 0.0299
-3.250 0.6026 0.04545 0.03900 -0.1758 0.5002 0.0305
-3.000 0.6246 0.04368 0.03720 -0.1772 0.4989 0.0316
-2.750 0.6991 0.03964 0.03269 -0.1929 0.4975 0.0360
-2.500 0.7172 0.03769 0.03079 -0.1932 0.4963 0.0370
-2.250 0.7492 0.03596 0.02902 -0.1964 0.4951 0.0395
-2.000 0.8010 0.03315 0.02595 -0.2041 0.4936 0.0448
-1.500 0.8813 0.02972 0.02221 -0.2125 0.4907 0.0557
-1.250 0.9264 0.02812 0.02033 -0.2172 0.4892 0.0651
-1.000 0.9806 0.02537 0.01707 -0.2226 0.4877 0.0454
-0.500 1.0693 0.02206 0.01281 -0.2288 0.4848 0.0237
-0.250 1.1039 0.02144 0.01195 -0.2302 0.4833 0.0224
0.000 1.1370 0.02105 0.01130 -0.2312 0.4820 0.0213
0.250 1.1686 0.02088 0.01097 -0.2321 0.4808 0.0208
0.500 1.2012 0.02068 0.01070 -0.2333 0.4796 0.0205
0.750 1.2318 0.02053 0.01060 -0.2341 0.4784 0.0204
1.000 1.2626 0.02048 0.01057 -0.2350 0.4770 0.0204
1.250 1.2934 0.02050 0.01060 -0.2359 0.4756 0.0205
1.500 1.3233 0.02058 0.01065 -0.2367 0.4740 0.0208
1.750 1.3530 0.02067 0.01071 -0.2373 0.4723 0.0215
2.000 1.3821 0.02078 0.01078 -0.2379 0.4706 0.0250
2.500 1.4542 0.02042 0.01168 -0.2423 0.4674 0.7315
2.750 1.4790 0.02060 0.01187 -0.2418 0.4661 0.7787
3.000 1.5018 0.02073 0.01202 -0.2408 0.4649 0.8251
3.250 1.5183 0.02074 0.01209 -0.2385 0.4638 0.8891
3.500 1.5370 0.02088 0.01232 -0.2369 0.4623 1.0000
3.750 1.5630 0.02124 0.01269 -0.2370 0.4606 1.0000
4.000 1.5891 0.02161 0.01306 -0.2371 0.4590 1.0000
4.250 1.6152 0.02197 0.01342 -0.2372 0.4575 1.0000
4.500 1.6411 0.02234 0.01378 -0.2373 0.4560 1.0000
4.750 1.6670 0.02269 0.01415 -0.2374 0.4546 1.0000
5.000 1.6929 0.02304 0.01449 -0.2375 0.4532 1.0000
5.250 1.7189 0.02338 0.01482 -0.2376 0.4519 1.0000
5.500 1.7450 0.02371 0.01513 -0.2377 0.4507 1.0000
5.750 1.7714 0.02403 0.01545 -0.2379 0.4495 1.0000
6.000 1.7983 0.02438 0.01576 -0.2382 0.4482 1.0000
6.250 1.8201 0.02487 0.01634 -0.2376 0.4466 1.0000
6.500 1.8400 0.02541 0.01700 -0.2367 0.4448 1.0000
6.750 1.8604 0.02595 0.01766 -0.2360 0.4431 1.0000
7.000 1.8811 0.02647 0.01827 -0.2352 0.4414 1.0000
7.250 1.9020 0.02697 0.01885 -0.2346 0.4398 1.0000
7.500 1.9232 0.02741 0.01935 -0.2339 0.4380 1.0000
7.750 1.9452 0.02777 0.01977 -0.2334 0.4363 1.0000
8.000 1.9683 0.02807 0.02010 -0.2330 0.4346 1.0000
8.250 1.9925 0.02836 0.02041 -0.2329 0.4331 1.0000
8.500 2.0160 0.02876 0.02084 -0.2327 0.4317 1.0000
8.750 2.0225 0.02969 0.02199 -0.2297 0.4293 1.0000
9.000 2.0300 0.03055 0.02305 -0.2269 0.4270 1.0000
9.250 2.0377 0.03137 0.02401 -0.2241 0.4250 1.0000
9.500 2.0474 0.03214 0.02490 -0.2217 0.4231 1.0000
9.750 2.0595 0.03285 0.02570 -0.2198 0.4214 1.0000
10.000 2.0741 0.03346 0.02641 -0.2183 0.4198 1.0000
10.250 2.0914 0.03399 0.02702 -0.2172 0.4184 1.0000
10.500 2.1115 0.03445 0.02754 -0.2166 0.4172 1.0000
10.750 2.0999 0.03639 0.02971 -0.2117 0.4146 1.0000
11.000 2.0777 0.03915 0.03272 -0.2062 0.4113 1.0000
11.250 2.0691 0.04137 0.03511 -0.2027 0.4083 1.0000
11.500 2.0735 0.04285 0.03670 -0.2008 0.4061 1.0000
11.750 2.0865 0.04377 0.03771 -0.1998 0.4043 1.0000
12.000 2.1109 0.04376 0.03775 -0.1997 0.4026 1.0000
12.250 1.9613 0.06062 0.05505 -0.1903 0.3923 1.0000
12.500 1.9773 0.06151 0.05602 -0.1899 0.3906 1.0000
12.750 2.0120 0.06010 0.05466 -0.1900 0.3894 1.0000
13.000 1.8705 0.08175 0.07652 -0.1879 0.3732 1.0000
13.250 1.9161 0.07837 0.07320 -0.1876 0.3739 1.0000
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Polar data table (+)
Polar graphs
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